Static load loading system and method in high-temperature thermal strength test for aerospace plane test

A technology for aerospace aircraft and strength testing, which is applied in the direction of aircraft component testing, machine/structural component testing, and measuring devices. It can solve problems affecting the accuracy of aircraft high-temperature thermal strength testing, and achieve test and research work promotion and connection stability. The effect of high and reliable equipment support

Active Publication Date: 2022-07-22
CHINA AIRPLANT STRENGTH RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] However, during the high-temperature thermal strength test of the aircraft, since the alloy steel or 304 stainless steel joints will block the radiation heating of the test piece, after the test, there will be obvious unheated areas on the surface of the test piece, which seriously affects the high temperature of the aircraft. Accuracy of heat strength test

Method used

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  • Static load loading system and method in high-temperature thermal strength test for aerospace plane test
  • Static load loading system and method in high-temperature thermal strength test for aerospace plane test
  • Static load loading system and method in high-temperature thermal strength test for aerospace plane test

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Experimental program
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Effect test

Embodiment 1

[0041] like figure 2 , 3 , The static load loading system in the high temperature thermal strength test for aerospace aircraft testing shown in 4 and 5 includes a bracket 1, an actuator 2 movably clamped on the bracket 1 and a static load threaded on the actuator 2. The loading assembly 3; the bracket 1 includes a base 10, four support rods 11 movably clamped on the base 10, and a limit plate 12 arranged above the base 10 and fixedly connected to the upper ends of the support rods 11 respectively; the base 10 is horizontal An adjustment slot 100 is provided, and an adjustment screw 101 is rotated and clamped inside the adjustment slot 100. The upper end surface of the base 10 is provided with a micro motor 102 that provides power for the adjustment screw 101; the limit plate 12 is provided with a strip-shaped through slot 120;

[0042] like figure 2 , 4 , 6, the bottom end of the actuator 2 is slidably connected with a compensation sleeve 20, and the bottom end of the com...

Embodiment 2

[0045] What this embodiment records is the loading method of the static load loading system in the high-temperature thermal strength test for the aerospace aircraft test of Embodiment 1, comprising the following steps:

[0046] S1. Connect the micromotor 102 and the actuator 2 to an external power supply respectively;

[0047] S2. According to the loading requirements of the static load in the high temperature thermal strength test of the aerospace aircraft, adjust the load loading angle of the actuator 2, then turn on the micro motor 102, and use the micro motor 102 to drive the adjustment screw 101 to rotate, so that the thread moves the seat 21 moves in the adjustment groove 100, at this time the bottom end of the actuator 2 moves with the thread moving seat 21 under the action of the compensation sleeve 20, and the top end of the actuator 2 swings in the bar-shaped through groove 120 on the limit plate 12;

[0048] S3. After the adjustment of the load loading angle of the ...

Embodiment 3

[0051] This embodiment differs from Embodiment 1 in that:

[0052] like figure 2 , 5 As shown in the figure, the upper end face of the base 10 is rotatably connected with a rotating disk 13, and the adjusting screw 101 and the micro motor 102 are both arranged on the rotating disk 13. The upper end surface of the base 10 and the outer side of the rotating disk 13 are provided with annular clamping grooves 14, each supporting The bottom ends of the rods 11 are all rotatably clamped with rotating rollers 110 that are movably clamped with the annular clamping grooves 14;

[0053] A fixing plate 15 is sleeved on the outer wall of the base 10 , and six mounting holes 150 are provided through the fixing plate 15 .

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PUM

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Abstract

The invention discloses a static load loading system and method in a high-temperature thermal strength test for aerospace aircraft testing, and belongs to the technical field of aircraft testing, the static load loading system comprises a support, an actuator clamped on the support and a static load loading assembly arranged on the actuator; the support comprises a base, a supporting rod connected to the base in a clamped mode and a limiting disc arranged above the base and connected with the supporting rod. The bottom end of the actuator is clamped on the base, and the top end penetrates through the limiting disc and is provided with a threaded hole; the static load loading assembly comprises a loading rod of which one end is connected with the threaded hole through an external thread joint and the other end is provided with an internal thread counter bore, a quartz glass bottom plate clamped at the end part of the loading rod, and a connecting screw rod which penetrates through the quartz glass plate and then is connected with the internal thread counter bore; the static load loading system is reasonable in structural design, the reliability and stability of the high-temperature thermal intensity test of the aerospace plane can be improved, and the loading precision of the thermal load in the test process can be improved.

Description

technical field [0001] The invention relates to the technical field of aircraft testing, in particular to a static load loading system and a method thereof in a high-temperature thermal strength test for aerospace aircraft testing. Background technique [0002] The aircraft high temperature thermal strength test is a key step in the aircraft structure test. The aircraft high temperature thermal strength test can observe and study the mechanical properties and resistance to damage of the aircraft structure or components in the thermal environment. During the test, it is necessary to simulate and fly on the ground. For the thermal load environment equivalent to the process, in addition to static, dynamic and fatigue tests in the thermal environment, it is also necessary to study the heat transfer test of the heat transfer characteristics of the structure, the thermal insulation test, the ground simulation test of ablation, and the creep. Tests, etc., according to the differenc...

Claims

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Application Information

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IPC IPC(8): B64F5/60G01M99/00
CPCB64F5/60G01M99/002G01M99/007G01M99/005
Inventor 王彬文张赐宝秦强丛琳华
Owner CHINA AIRPLANT STRENGTH RES INST
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